Numerical Simulation of the Thermal State of the Turbine Nozzle Guide Vane of a Modern Gas Turbine Engine

Numerical modeling to determine the thermal state of the cooled nozzle vane of the first stage of a high-pressure turbine (HPT) and its refinement is an important process of modern design of gas turbine engines (GTE), since the problem of effective cooling at gas temperatures higher than 2200 K, taking into account the circumferential imbalance at the combustion chamber outlet, becomes one of the key ones. To confirm the operability of the nozzle vane of the first stage of the HPT, coupled simulation was performed taking into account the most extreme conditions of the engine operation. On the basis of data obtained from the calculation of turbine aerodynamics in the Numeca software package and modeling of the combustion chamber operating process, the thermal state of the nozzle vane of the first stage of the HPT was calculated and it was improved in the climb stage of the installed engine, taking into account the heavy weather conditions. The obtained data confirm the possibility of operation of the designed nozzle vane.